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Target orbit modification via gas-blastTarget orbit modification via gas-blast description/claimsThe Patent Description & Claims data below is from USPTO Patent Application 20070285304, Target orbit modification via gas-blast. Brief Patent Description - Full Patent Description - Patent Application Claims
CROSS-REFERENCE TO RELATED APPLICATIONS [0001] This application claims the benefit of provisional application No. 60/783,658, filed Mar. 16, 2006, the disclosure and appendices of which are hereby incorporated by reference herein, in their entirety, for all purposes. BACKGROUND [0002] 1. Technical Field [0003] The invention, it its several embodiments, pertains to orbit debris relocation and the present field of endeavor more particularly pertains to methods, systems and apparatuses adapted to impart orbital changes to satellites, orbital debris, and other orbital targets via directed gas. [0004] 2. State of the Art [0005] State of the art space debris clearing includes the use of explosive charges, or shaped energetics to impart an impulse on the intended field of space to change their velocities and orbits. The resulting explosion may have the debris shifted to a higher orbit or diverted into a decaying orbit resulting in incineration on atmospheric re-entry. State of the art space debris clearing includes an apparatus that mechanically impacts and adheres to the impact debris and includes an apparatus that mechanically grapples the debris and has the apparatus and grappled cargo incinerated upon atmospheric re-entry. Another state of the art space debris clearing apparatus imparts electromagnetic energy upon targeted debris until a level of disintegration of the debris is achieved. SUMMARY [0006] The invention, in its several embodiments includes a system comprising a rocket motor adapted to produce directed exhaust gas particles; a targeting system adapted to determine a first aim point for the directed exhaust; and an attitude control system adapted to orient the rocket motor in response to the determined first aim point. In other embodiments of the invention the system may further comprise a thrust-reversing element adapted to deflect a portion of the directed exhaust, which may in some embodiments comprise a fuselage, the fuselage housing at least a portion of the rocket motor wherein the thrust-reversing element is a steel foil attached to the fuselage via three or more suspension lines. In other embodiments of the invention the system may comprise a fuselage wherein the targeting system includes a radar system proximate to the fuselage, which may in some embodiments comprise a fuselage wherein the propellant of the rocket motor is seeded to exhaust radar-reflective particles. In other embodiments of the invention the system may further comprise a fuselage wherein the targeting system is adapted to process radar returns from a plurality of gas particles proximate to the target space object and there from determine a second aim point. In other embodiments of the invention the system may also be a system comprising an exo-atmospheric vehicle adapted to produce a directed gas-blast via a frangible nosecone; and a targeting system adapted to determine an aim point for the directed gas-blast. [0007] The invention, in its several embodiments also includes a method of imparting momentum to a target space object comprising an exhaust gas generator proximate to the target space object wherein the exhaust gas generator is adapted to expel generated gas according to a trajectory, and directing a first blast of expelled generated gas wherein at least a portion of the trajectory of the first blast of expelled generated gas impinges on the target space object. Other embodiments of the invention may include a method of imparting momentum to a target space object providing an exhaust gas generator proximate to the target space object wherein the exhaust gas generator is adapted to expel generated gas according to a trajectory, and directing a first blast of expelled generated gas wherein at least a portion of the trajectory of the first blast of expelled generated gas impinges on the target space object which may in some embodiments comprise determining an aim point for a second blast of expelled generated gas based on radar returns from a plurality of expelled gas particles proximate to the target space object and directing a second blast of expelled generated gas wherein at least a portion of the trajectory of the second blast of expelled generated gas impinges on the target space object. In other embodiments of the invention, the method may further comprise deflecting a portion of the expelled generated gas via a thrust reversing element. In still other embodiments of the invention, the method may further comprise deploying a thrust reversing element comprising steel foil into the trajectory of the first blast of expelled generated gas. In other embodiments of the invention, the method may include the expelled generated gas of at least the first blast to be comprised of radar-reflective particles. BRIEF DESCRIPTION OF THE DRAWINGS [0008] For a more complete understanding of the present invention and for further features and advantages, reference is now made to the following description taken in conjunction with the accompanying drawings, in which: [0009] FIG. 1 illustrates an exemplary depiction of an example of a gas blast delivering an impulse to a satellite whose orbit is to be elevated; [0010] FIG. 2 illustrates and exemplary interceptor missile's direct ascent encounter trajectory which aims a rocket engine exhaust gas-blast at target, according to an embodiment for the invention; [0011] FIG. 3 illustrates cooling of various sized carbon exhaust particles with distance for a 6000 ft/sec rocket exhaust velocity, according to an embodiment for the invention; [0012] FIG. 4 is an exemplary interceptor missile design to use aimed, space-chilled exhaust of its own propulsion rocket motor as the gas-blast generator, according to an embodiment for the invention; [0013] FIG. 5A illustrates a target satellite silhouette imaged using impingement of radar-scattering particles in rocket exhaust, according to an embodiment for the invention; [0014] FIG. 5B shows a target satellite profile superimposed on a radar resolution cell grid, according to an embodiment for the invention; [0015] FIG. 6A shows an example of radar cell imagery, according to an embodiment for the invention; [0016] FIG. 6B shows an example of radar cell imagery, according to an embodiment for the invention; [0017] FIG. 7 illustrates that the Doppler radar determines target approach & rotation; [0018] FIG. 8 shows an example of an interceptor missile encountering a satellite during a formation flight co-orbit trajectory, according to an embodiment for the invention; [0019] FIG. 9 shows an example of an interceptor missile delivering orbit-changing impulse to a satellite to lift its orbit, according to an embodiment for the invention; [0020] FIG. 10 is an example of an interceptor missile blowing debris out of orbit, according to an embodiment for the invention; Continue reading about Target orbit modification via gas-blast... Full patent description for Target orbit modification via gas-blast Brief Patent Description - Full Patent Description - Patent Application Claims Click on the above for other options relating to this Target orbit modification via gas-blast patent application. ###  How KEYWORD MONITOR works... a FREE service from FreshPatents1. Sign up (takes 30 seconds). 2. Fill in the keywords to be monitored. 3. Each week you receive an email with patent applications related to your keywords. Start now! - Receive info on patent apps like Target orbit modification via gas-blast or other areas of interest. ### Previous Patent Application: Step frequency high resolution radar Next Patent Application: Verified distance ranging Industry Class: Communications: directive radio wave systems and devices (e.g., radar, radio navigation) ### FreshPatents.com Support Thank you for viewing the Target orbit modification via gas-blast patent info. 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